NACA 23018 (naca23018-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23018 (naca23018-il) Reynolds number: 100,000 Max Cl/Cd: 38.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23018-il-100000-n5.txt Download as CSV file: xf-naca23018-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8879 0.09200 0.08481 -0.0486 1.0000 0.0563
-16.500 -0.9254 0.08335 0.07587 -0.0535 1.0000 0.0565
-16.250 -0.9281 0.07987 0.07234 -0.0547 1.0000 0.0570
-16.000 -0.9369 0.07574 0.06809 -0.0563 1.0000 0.0575
-15.750 -0.9470 0.07163 0.06384 -0.0577 1.0000 0.0580
-15.500 -0.9571 0.06770 0.05975 -0.0587 1.0000 0.0585
-15.250 -0.9661 0.06403 0.05590 -0.0594 1.0000 0.0591
-15.000 -0.9738 0.06064 0.05232 -0.0597 1.0000 0.0598
-14.750 -0.9804 0.05749 0.04896 -0.0597 1.0000 0.0605
-14.500 -0.9864 0.05454 0.04578 -0.0593 1.0000 0.0613
-14.250 -0.9925 0.05175 0.04270 -0.0584 1.0000 0.0621
-14.000 -0.9855 0.04988 0.04077 -0.0577 1.0000 0.0630
-13.750 -0.9756 0.04834 0.03922 -0.0568 1.0000 0.0639
-13.500 -0.9672 0.04673 0.03756 -0.0559 1.0000 0.0649
-13.250 -0.9591 0.04510 0.03583 -0.0548 1.0000 0.0660
-13.000 -0.9510 0.04348 0.03406 -0.0535 1.0000 0.0672
-12.750 -0.9434 0.04189 0.03228 -0.0521 1.0000 0.0685
-12.500 -0.9305 0.04058 0.03094 -0.0509 1.0000 0.0697
-12.250 -0.9169 0.03945 0.02984 -0.0497 1.0000 0.0709
-12.000 -0.9047 0.03831 0.02866 -0.0483 1.0000 0.0723
-11.750 -0.8922 0.03717 0.02745 -0.0468 1.0000 0.0738
-11.500 -0.8797 0.03607 0.02623 -0.0452 1.0000 0.0754
-11.250 -0.8667 0.03504 0.02521 -0.0435 1.0000 0.0769
-11.000 -0.8551 0.03412 0.02433 -0.0416 1.0000 0.0784
-10.750 -0.8448 0.03324 0.02345 -0.0395 1.0000 0.0802
-10.500 -0.8352 0.03241 0.02257 -0.0370 1.0000 0.0821
-10.250 -0.8264 0.03165 0.02174 -0.0343 1.0000 0.0840
-10.000 -0.8217 0.03090 0.02106 -0.0309 1.0000 0.0855
-9.750 -0.8191 0.03026 0.02045 -0.0271 1.0000 0.0872
-9.500 -0.8172 0.02968 0.01987 -0.0230 1.0000 0.0893
-9.250 -0.8129 0.02910 0.01925 -0.0193 1.0000 0.0916
-9.000 -0.8100 0.02848 0.01866 -0.0154 1.0000 0.0937
-8.750 -0.8073 0.02790 0.01811 -0.0114 1.0000 0.0960
-8.500 -0.8033 0.02736 0.01757 -0.0077 1.0000 0.0989
-8.250 -0.7981 0.02686 0.01703 -0.0040 1.0000 0.1022
-8.000 -0.7924 0.02625 0.01648 -0.0007 0.9995 0.1056
-7.750 -0.7585 0.02546 0.01567 -0.0026 0.9931 0.1130
-7.500 -0.7276 0.02458 0.01485 -0.0040 0.9856 0.1220
-7.250 -0.6950 0.02373 0.01407 -0.0057 0.9790 0.1346
-7.000 -0.6665 0.02287 0.01332 -0.0066 0.9704 0.1520
-6.750 -0.6373 0.02192 0.01260 -0.0076 0.9628 0.1815
-6.500 -0.6100 0.02097 0.01199 -0.0083 0.9542 0.2312
-6.250 -0.5817 0.02025 0.01155 -0.0089 0.9458 0.2858
-6.000 -0.5505 0.01972 0.01121 -0.0098 0.9375 0.3322
-5.750 -0.5206 0.01932 0.01093 -0.0103 0.9286 0.3670
-5.500 -0.4894 0.01899 0.01065 -0.0108 0.9195 0.3968
-5.250 -0.4598 0.01870 0.01042 -0.0110 0.9099 0.4218
-5.000 -0.4296 0.01841 0.01019 -0.0112 0.9000 0.4481
-4.750 -0.4022 0.01818 0.01000 -0.0108 0.8891 0.4740
-4.500 -0.3721 0.01792 0.00980 -0.0109 0.8790 0.4988
-4.250 -0.3463 0.01773 0.00968 -0.0100 0.8665 0.5217
-4.000 -0.3152 0.01749 0.00951 -0.0101 0.8565 0.5455
-3.750 -0.2902 0.01733 0.00938 -0.0091 0.8422 0.5649
-3.500 -0.2613 0.01713 0.00916 -0.0088 0.8298 0.5821
-3.250 -0.2314 0.01693 0.00897 -0.0085 0.8166 0.5955
-3.000 -0.2040 0.01677 0.00880 -0.0080 0.8015 0.6088
-2.750 -0.1757 0.01660 0.00858 -0.0076 0.7870 0.6237
-2.500 -0.1453 0.01644 0.00840 -0.0074 0.7728 0.6373
-2.250 -0.1183 0.01634 0.00829 -0.0067 0.7556 0.6517
-2.000 -0.0913 0.01625 0.00815 -0.0060 0.7384 0.6672
-1.750 -0.0633 0.01619 0.00807 -0.0054 0.7211 0.6820
-1.500 -0.0351 0.01616 0.00799 -0.0049 0.7036 0.6968
-1.250 -0.0077 0.01614 0.00791 -0.0042 0.6859 0.7123
-1.000 0.0189 0.01615 0.00784 -0.0035 0.6679 0.7286
-0.750 0.0470 0.01621 0.00789 -0.0030 0.6493 0.7426
-0.500 0.0744 0.01628 0.00791 -0.0024 0.6312 0.7575
-0.250 0.1008 0.01635 0.00791 -0.0017 0.6137 0.7732
0.000 0.1295 0.01648 0.00799 -0.0013 0.5965 0.7870
0.250 0.1580 0.01663 0.00805 -0.0009 0.5796 0.8005
0.500 0.1844 0.01676 0.00809 -0.0002 0.5631 0.8153
0.750 0.2142 0.01696 0.00825 -0.0001 0.5459 0.8274
1.000 0.2426 0.01714 0.00836 0.0001 0.5293 0.8400
1.250 0.2696 0.01733 0.00847 0.0006 0.5135 0.8535
1.500 0.3014 0.01759 0.00864 0.0002 0.4972 0.8635
1.750 0.3271 0.01778 0.00876 0.0009 0.4813 0.8767
2.000 0.3611 0.01806 0.00898 -0.0001 0.4644 0.8854
2.250 0.3881 0.01829 0.00913 0.0002 0.4490 0.8974
2.500 0.4226 0.01859 0.00934 -0.0009 0.4330 0.9055
2.750 0.4505 0.01885 0.00950 -0.0009 0.4183 0.9167
3.000 0.4864 0.01915 0.00975 -0.0025 0.4024 0.9240
3.250 0.5154 0.01942 0.00996 -0.0027 0.3884 0.9345
3.500 0.5538 0.01975 0.01019 -0.0049 0.3742 0.9406
3.750 0.5837 0.02005 0.01043 -0.0055 0.3617 0.9505
4.000 0.6233 0.02038 0.01070 -0.0081 0.3488 0.9559
4.250 0.6556 0.02072 0.01094 -0.0093 0.3383 0.9645
4.500 0.6932 0.02103 0.01125 -0.0115 0.3269 0.9704
4.750 0.7275 0.02140 0.01153 -0.0132 0.3179 0.9777
5.000 0.7643 0.02172 0.01186 -0.0154 0.3081 0.9837
5.250 0.7997 0.02211 0.01215 -0.0174 0.3001 0.9901
5.500 0.8365 0.02245 0.01254 -0.0197 0.2915 0.9957
5.750 0.8681 0.02284 0.01285 -0.0210 0.2847 1.0000
6.000 0.8831 0.02316 0.01318 -0.0190 0.2790 1.0000
6.250 0.8976 0.02349 0.01353 -0.0170 0.2731 1.0000
6.500 0.9115 0.02384 0.01384 -0.0148 0.2678 1.0000
6.750 0.9253 0.02422 0.01420 -0.0126 0.2624 1.0000
7.000 0.9383 0.02458 0.01461 -0.0102 0.2563 1.0000
7.250 0.9510 0.02495 0.01495 -0.0078 0.2510 1.0000
7.500 0.9643 0.02539 0.01533 -0.0056 0.2463 1.0000
7.750 0.9766 0.02580 0.01584 -0.0031 0.2410 1.0000
8.000 0.9890 0.02623 0.01628 -0.0007 0.2362 1.0000
8.250 1.0021 0.02668 0.01669 0.0016 0.2321 1.0000
8.500 1.0148 0.02719 0.01723 0.0039 0.2279 1.0000
8.750 1.0263 0.02770 0.01782 0.0064 0.2233 1.0000
9.000 1.0379 0.02820 0.01833 0.0088 0.2190 1.0000
9.250 1.0507 0.02872 0.01881 0.0110 0.2153 1.0000
9.500 1.0617 0.02933 0.01949 0.0134 0.2111 1.0000
9.750 1.0713 0.02995 0.02020 0.0160 0.2067 1.0000
10.000 1.0804 0.03053 0.02082 0.0186 0.2028 1.0000
10.250 1.0919 0.03114 0.02138 0.0207 0.1993 1.0000
10.500 1.1000 0.03192 0.02227 0.0232 0.1954 1.0000
10.750 1.1076 0.03275 0.02321 0.0255 0.1911 1.0000
11.000 1.1170 0.03354 0.02404 0.0275 0.1872 1.0000
11.250 1.1291 0.03431 0.02476 0.0290 0.1839 1.0000
11.500 1.1343 0.03547 0.02610 0.0310 0.1798 1.0000
11.750 1.1407 0.03662 0.02736 0.0327 0.1758 1.0000
12.000 1.1488 0.03769 0.02845 0.0342 0.1723 1.0000
12.250 1.1589 0.03873 0.02947 0.0354 0.1691 1.0000
12.500 1.1594 0.04046 0.03143 0.0369 0.1652 1.0000
12.750 1.1628 0.04206 0.03313 0.0380 0.1615 1.0000
13.000 1.1688 0.04349 0.03458 0.0389 0.1583 1.0000
13.250 1.1736 0.04513 0.03626 0.0396 0.1553 1.0000
13.500 1.1691 0.04767 0.03901 0.0403 0.1516 1.0000
13.750 1.1681 0.04996 0.04140 0.0406 0.1482 1.0000
14.000 1.1718 0.05184 0.04329 0.0408 0.1452 1.0000
14.250 1.1679 0.05466 0.04622 0.0408 0.1422 1.0000
14.500 1.1560 0.05850 0.05027 0.0402 0.1390 1.0000
14.750 1.1496 0.06185 0.05373 0.0395 0.1360 1.0000
15.000 1.1519 0.06422 0.05609 0.0391 0.1333 1.0000
15.250 1.1372 0.06893 0.06097 0.0377 0.1307 1.0000
15.500 1.1098 0.07571 0.06800 0.0351 0.1279 1.0000
15.750 1.0894 0.08179 0.07423 0.0326 0.1252 1.0000
16.000 1.0922 0.08447 0.07690 0.0317 0.1228 1.0000
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Polar data table (+)
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